A method has been developed for computing aerodynamic loads on slender missiles with complicated cross‐sections. This method has been applied to the prediction of loads for missiles with folding wings. Comparison of theoretical calculations with supersonic wind‐tunnel measurements indicates that the method should provide satisfactory first estimates of the aerodynamic properties of missiles with folding wings. A series of design charts is presented to allow rapid estimation of lift, folding moment and span loading for a wide variety of folding‐wing configurations.